Radio controlled rocket



Dec. 12, 1961 M. l. HULL RADIO CONTROLLED ROCKET 3 Sheets-Sheet 1Original Filed Jan. 8, 1942 FIG.1.

9 4 v 5 5 2 Ga 4 I F 1 5 2 5 2 FIG.3.

VII

48 INVENTOR.

I VIAURY I. HULL jzwldw Dec. 12, 1961 M. I. HULL 3,012,739

RADIO CONTROLLED ROCKET Original Filed Jan. 8, 1942 3 Sheets-Sheet 2 INV EN TOR.

IyIAURY I. HULL United States Patent Ofifice Patented ec. l2, 19%1 Thisinvention relates to .a guided missile having new and novel structuralfeatures which enable the missile to be fully controlled throughout theentire trajectory thereof from a control station remote therefrom. Morespecifically, this invention is directed to a rocket which may beparticularly useful in some types of warfare such, for example, as inanti-aircraft defense and which may be entirely controlled in flight byradio waves of predetermined frequency.

This is a divisional application of my copending application Serial No.426,086, filed January '8, 1942, and

now Patent Number 2,994,270, which is a continuationin-part of my parentcase Serial No. 377,398, filed,

January 21, 1941, now abandoned.

It has been found desirable in the art of guided missiles to control themissile by some form of radiant energy such, for example, as unmodulatcdlight, modulated light, spectra controlled light, or radio, or anycombination of these forms of radiant energies. Of these forms, it hasbeen found that, in general, the structure required for the completecontrol of a missile by radio is of less 7 complexity and the rocket maybe manufactured with greater economy than that structure utilized inrockets using the other forms of radiant energy, hereinbefore mentioned.The simplicity of radio controlled rockets in relation to rockets usingthe majority of other forms of radiant energy resides in the fact thatthe latter type of rockets must contain structure which will eliminateor counteract the interference of non-controlling searchlights or theeffects of passing clouds, smoke, and the light from exploding shells,and the elfect of the light of the sun. Rockets controlled by a radiobeam, however, may be fully operative and yet have .none of this complexstructure for eliminating or counteracting such interferences andundesired effects.

Accordingly, one of the objectsof this invention is the provision of anew and novel rocket which may be directed to the target by theselective utilization of radio waves of predetermined frequencies.

Another object of the instant invention is to provide a radio controlledrocket which is equipped with a charge of high explosive in the tailthereof, the release of this charge being controlled by a radio signalof predetermined frequency. f

Still another object is the provision of a rocket which is equipped withan electrically operated fuze capable of being activated in response toasignal of predetermined radio frequency.

Still another object of the instant invention is the provision in acombination radiant energy guided rocket of new and improved means forfiring the rocket either in response to a predetermined radiant energysignal or by actual contact with enemy aircraft or other target.

Other objects and many of the attendant advantages of this inventionwill be readily appreciated as the same becomes better understood byreference to the following detailed description when considered inconnection with the accompanying drawings wherein:

FIG. 1 is an elevational view shown partly in section to illustrate someof the interior elements of a rocket in accordance with one form of myinvention in which the rocket is steered by selectively pointing theexhaust vent thereof and in which apparatus for throwing a charge ofexplosive from the rocket at a selected time is included;

FIG. '2 is a view of the rocket taken on line 2-2 of FIG. 1;

FIG. 3 is a sectional view of an electrically controlled fuze which mayhoused in conjunction with the rocket of the instant invention;

FIG. 4 is a diagrammatic showing of a control circuit which may beutilized with the rocket shown in FIG. 1 and which includes radiofrequency circuitry whereby the rocket maybe controlled in flight from aradio transmitting station by remote control; and

PEG. 5 illustrates in diagrammatic form a radio transmitting circuit ata control station which may be utilized for transmitting radio signalsto the receiving and rocket controlling circuit of FIG. 4.

Referring now to the accompanying drawings in which like referencenumerals are employed to designate like parts, and more particularly toFIG. 1 thereof in which reference numeral 11 generally designates therocket in accordance with a form of my invention it will be observedthat the direction of flight .of the rocket is changed by changing theangular setting of the exhaust vent of the combustion chamber relativeto the longitudinal axis of the rocket; The rocket of this form of myinvention preferably has four posts or supports 12, 13, 14, and 15 whichmay be joined to the forward and rearward portions of the rocket,respectively, in any convenient manner such, for example, as by welding.An antenna 16 which may be of any desired construction such, forexample, as comprising an insulated wire running along the side of therocket and attached thereto so that the rocket will be capable ofreceiving radio signals which are transmitted from a remote controlstation located, for example, on the earth. Combustion chamber 17 ismounted in the center of the metal plate 13 which may also serve as thefloor of the chamber 19 containing an explosive charge 10. A piece ofspring metal 21 connecting the exhaust vent 22 and combustion chamber 17to plate 18 enables the chamber and exhaust vent to be moved slightlyoff the longitudinal axis of the rocket by one of the magnets shown inFIG. 2, to be more fully explained hereinafter. At 23 and 24 are shownconnections which may be of any suitable type such, for example, asordinary steam hose and which connect the combustion chamber 17 with thepipe, 25 and with the pipe 26, respectively, which bring the fuel andoxidizing material to the combustion chamber 17 from the liquid oxygenchamber 27 and the fuel chamber 28. Between chambers 27 and 28 isarranged a piston 2G with one or more piston rings 30. The pressure 'ofthe liquid oxygen or other liquid under a relatively high pressure incompartment 27 against the piston 26 maintains an approximately equalpressure on the alcohol or other liquid fuel in chamber 28 therebyforcing the liquid in this last mentioned chamber up the pipe 26 andinto the combustion chamber 17. A circular ring 29 connects the fourposts, hereinbefore mentioned, upon which the magnets 31, 32, 33, and 34are mounted.

A large cylinder of explosive and shrapnel 35 is releasably mountedwithin the tail portion of the rocket and is arranged to be releasedupon the energization of solenoid 36. It is intended that the head orupper end portion of the rocket contain only enough explosive toeffectively cripple or destroy an aircraft provided the rocket actuallyhit the aircraft and is detonated by the contact fuze or striker head 37which is described in greater detail in my copending application Scr.No. 426,086, hereinbefore mentioned. The main body of explosive will bethat designated by numeral35. The arm 38 which is attached to the mainbody of explosive 35 passes upwardly through an opening in rib 39.Spring 41 to which is attached a metallic member 42 normally pressesagainst arm 38 with suflicient pressure to force this arm downwardly andoutwardly, as viewed in the drawing, in a rapid fashion. A latchconsisting of rod 43 with flange 44 is provided with a spring 45pressing against the flange thereby tending to force the rod 43 into arecessed portion 46 of arm 38 to prevent movement thereof until thelatch is released. The latch is constructed and arranged to be operatedby magnet 36 which, when energized, pulls the rod 43 into the solenoid36 and thereby releases the arm 33. As the charge 35 is forced outwardlyof the casing of the rocket by spring 41, the element 47 which is thecontrol of a time delay fuze of any convenient design, trips against theelement 43 thereby activating the fuze and exploding the charge 35 afterthe rocket has moved a predetermined number of yards from that point onthe trajectory where the fuze was activated. Compartments 49 and 51 areprovided for the accommodation of electrical apparatus, hereinafter tobe more fully explained.

F16. 2 is a view of the steering arrangement looking upwardly from line2-2 in FIG. 1. The magnets 31, 32, 33 and 34 are arranged to exertpulling effects upon metallic pieces 52, 53, 54 and 55 which are mountedupon the exhaust vent 22 and which are best seen in FIG. 2. Thesemetallic pieces are attached to the exhaust vent 22 in any suitablemanner such, for example, as by welding. Springs 56, 57, 58 and 59, FIG.2, tend to maintain the exhaust vent in alignment with the longitudinalaxis of the rocket when none of the magnets are energized, and returnthe exha 1st vent to the aligned position when all of the magnets arede-energized. All of the electromagnets and solenoids shown in FIGS. 1and 2 are controlled by a circuit such, for example, as that illustratedin FIG. 4, to be described hereinafter, and on which these elements areshown diagrammatically.

Referring now to FIG. 3 wherein the electrically controlled fuze, towhich reference has been made hereinbefore, is shown in cross sectionand which is generally designated by numeral 61, it will be understoodthat this fuze may occupy any convenient space in compartment 19 of therocket such, for example, as being fastened to the fioor 18 of thiscompartment. The primer or detonator charge is designated in FIG. 3 bynumeral 62. The fuze casing 63 is provided with flash hole 64 therebyproviding direct communication between the primer charge 62 and the mainexplosive charge contained in compartment 19 of the rocket. The firingpin 65 is normally held away from the primer charge due to the fact thata groove 66 in pin 65 is engaged by rod 67 in the manner shown. Thiscoaction between rod 67 and pin 65 prevents the spring 68 which pressesagainst flange 69 of pin 65 from forcing the pin 65 forward into theprimer charge until rod 67 is withdrawn. When rod 67 is withdrawn frompin 65, the spring 63 forces the firing pin 65 into the primer charge.When the firing pin 65 strikes the primer charge 62 an explosiveresults, the flash of which passes through flash hole 64 and detonatesthe main charge in compartment 19 of the rocket. Rod 67 is normally heldin the groove of pin 65 by spring 71 pressing against a circular flange72. However, when solenoid magnet 73 becomes energized by currentflowing from battery 40, shown in FIG. 4, as will more clearly appear asthe description proceeds, rod 67 moves upwardly against thecompressional force of spring 71 thereby releasing pin 65 and causingthe primer charge 62 to be exploded.

FIG. 4 which combines certain portions of FIGS. 21 and 22 of mycopending application, hereinbefore identified, will now be described,As will be more fully understood as the description proceeds, thiscircuit permits energization of the magnets hereinbefore mentioned uponthe transmission of radio signals of predetermined frequencies whichreach the antenna 16 and which are transmitted from a control station.The antenna 16 is coupled to tube 74 by transformer 75 with a condenser76 for proper tuning, and a battery 77 is provided to supply a grid biasto tube 74. When biased, tube 74 acts as a detector or rectifier and theplate circuit thereof contains the radio frequency filter comprisingchoke 78 which suppresses radio frequency components of plate current.Condensers 79 and 81 are also provided in the plate circuit of tube '74.Plate potential for tube 74 is supplied by battery 82, and the audiofrequency choke 83 supplies the load across which the audio frequencyvoltage is developed. Choke 83 has a high impedance at the lowest audiofrequency to be used. When switch 84 is closed, the cathode or filamentof tube 74 is connected to the cathode or filament of tube 85, and whenswitch S6 is closed one side of the choke 83 is connected to one side ofthe coupling condenser 87. Therefore, the rectified output of tube 74 ispassed on to tube 85 and may operate a selected one of the relays 83,89, 91, 92 and 93 in the plate circuit of tube 85 when the radio wavereaching antenna 16 is modulated at the predetermined audio frequency atwhich the particular relay is responsive. Whereas FIG. 4 does not showthe solenoid 73 and instead shows solenoid 36, it will be obvious to oneskilled in the art that either of these solenoids may be substituted forthe other or, should it be desired to use both of these solenoids in thecircuit, another relay such, for example, as those shown in FIG. 4 maybe added to the circuit without departing from the spirit and scope ofthe invention.

FIG. 5 shows the radio frequency transmitting circuit at a controlstation for supplying the frequency modulated radio wave which willproperly operate the radio controlled circuit of FIG. 4. The antenna andground are shown at 94 and 95, respectively, the antenna coupling coilat 96, and the primary tuning inductance being shown at 97. The circuitof tube 98 may be a simple Hartley oscillator circuit having grid leakbias and a transformer in the filament return for introducing amodulating frequency. The condenser 99 by-passes radio frequency. Audiofrequency generators of any desirable type such, for example, as vacuumtube oscillators employing transformer feedback are shown at 101, 102,103, 104, 105, 106 and 107. While only five of these audio frequencygenerators are required to operate the electroresponsive devices 31, 32,33, 34 and 36 of FIG. 4, it will be understood that additionalgenerators such, for example, as those shown in FIG. 5 at 106 and 107may be provided, for the purpose of activating additionalelectroresponsive control elements, not shown. The output of these audiofrequency generators may be connected to the primary 108 of thetransformer 109 in the filament return of the radio frequency generatortube 98 through variable resistance 111 by closing the appropriateswitch of the switch group 112, 113, 114, 115, 116, 117 and 118. Thefrequencies of the audio generators are such as to be appropriate tooperate the relays 88, 89, 91, 92 and 93 of FIG. 4 selectively, each ofwhich is responsive to a different frequency. The audio generators maybe so chosen as to contain means for varying their frequencie withinnecessary limits such, for example, as tapped transformers.

While the operation of the device has been described with particularreference to steering the rocket by energization of a single one of thesolenoids 31-34, it will be understood that, if desired, additionalsteering control may be obtained by simultaneously energizing anadjacent pair of these solenoids, it being merely necessary to close theproper pair of switches 112-116, FIG. 5, at the control station.

It will be obvious to those skilled in the art that other types ofelectron tubes having equivalent functions to the types of tubesdisclosed herein may be utilized in lieu of the disclosed tubes. It willalso be understood that amplifiers may be added in situations in whichit is desired to increase the range of the rocket. Likewise, dry fuelsof a suitable type may be utilized instead of the liquid fuels hereindisclosed. It is obvious that simple devices of electrical or mechanicalnature such, for example, as levers may be utilized to provide amechanical advantage for the action of the magnets hereinbeforedisclosed.

While the invention has been described herein with reference to acertain preferred example thereof which gives satisfactory results, itwill be understood :by those skilled in the art to which the inventionpertains, after understanding the invention, that variou changes andmodifications may be made without departing from the spirit and scope ofthe invention, and it is my intention, therefore, to cover in theappended claims all-such changes and modifications.

The invention herein described and claimed may be manufactured and usedby or for the Government of the United States of America forgovernmental purposes without payment of any royalties thereon ortherefor.

What is claimed as new and desired to be secured by Letters Patent ofthe United States is:

1. In apparatus of the character disclosed, the combination of a rocketbody having a chamber therein, an explosive charge carried within saidchamber and adaptedto be forcibly ejected therefrom, a spring urgedmember operatively associated with an initially compressed spring fordriving said member upon extension thereof, said member being mounted inabutting relation With said charge Within said chamber for impartinginstantaneous force directly to said charge to forcibly eject saidcharge, a latch mechanism associated with said spring and adapted tonormally maintain said spring in compressed position and maintain saidcharge within said chamber, a solenoid operatively associated with saidlatch mechanism and adapted when energized to operate said latchmechanism and thereby release said spring and charge, radiant energysensitive means mounted on said body, and circuit means in said rocketbody and including a source of electrical power interconnecting saidradiant energy sensitive means and said solenoid for energizing saidsolenoid whereby said charge is ejected when radiant energy havingpredetermined characteristics reaches said radiant energy sensitivemeans.

2. A rocket including a frame fixed relative thereto and having alongitudinal axis, means forming a combustion chamber, means forsupplying combustible material to said chamber for ignition therein toproduce expansive gases which impart directional inertia to the rocket,a nozzle secured to said chamber and forming an exhaust vent for saidgases to determine the direction of said directional inertia, means forpivotally mounting said chamber-forming means on said frame andencompassed therewithin, resilient means secured to said frame andengaging said chamber-forming means for yieldably urging the nozzle intoalignment with said longitudinal axis, .a ,plurality ofelectroresponsive devices mounted at spaced intervals upon said frameand *operabl-e upon selective energization thereof to correlativelydeflect said chamberforming means from said axis thereby to change theangular setting of said nozzle with respect to said axis selectively inaccordance with the energization of said devices, a radio wave receivingantenna mounted on said frame, and electrical means interconnecting saidantenna and said electroresponsive devices for selectively energizingthe electroresponsive devices and thereby changing the setting of saidnozzle with respect to said axis in accordance with a predeterminedfrequency of radio signal reaching said antenna, said resilient meansbeing effective to restore said chamber-forming means with the attachednozzle to said longitudinal axis upon de-energization of said devices. 7

3. A rocket including a frame fixed relative thereto and having alongitudinal axis, means forming a combustion chamber, means forsupplying combustible material to said chamber for ignition therein toproduce expansive gases which impart directional inertia "to the rocket,a :nozzle secured to said chamber and forming an exhaust vent for saidgases to determine the direction of said directional inertia, meanspivotally mounting said chamber- Iforming means and nozzle upon saidframe and encompassed :therewithin with the nozzle normally arranged inalignment with said longitudinal axis, four electroresponsive devicesmounted in substantially equally spaced peripheral intervals upon saidframe andoperable upon selective energization thereof to correlativelydeflect said chamber-forming means from said axis thereby to change theposition of said nozzle with respect to said axis selectively inaccordance with the energization of said devices, means for returningsaid nozzle to its original aligned position when said devices arede-energized, an antenna mounted upon said rocket, a detectorelectrically connected on the input side thereof, to said antenna,anamplifier having the input side thereof electrically connected .to theoutput side of said detector, a plurality of relays electricallyconnected to the output side of said amplifier, said relays beingadapted to be energized selectively in accordance with predeterminedradio wave frequencies and being operatively connected to andcontrolling the energization of said 'electroresponsive devices wherebythe position of said nozzle is controlled by radio waves of saidpredetermined frequencies reaching the antenna.

4. 'In apparatus of the character disclosed, in combination, a rocketbody having a chamber therein, said chamber having a charge of explosivereleasably supported therein, a'spring urged member operativelyassociated with anormally compressed spring for driving said member uponrelease thereof, said memberbeing mounted Within said chamber inabutting relation with said charge and adapted when said compressedspring is released to force said charge outside said chamber, latchingmeans for. normally maintaining said spring in compressed position andsaid charge Within the chamber, a solenoid operatively associated withsaid latching means and adapted when energized .to release the latchingmeans, a radio antenna mounted on said body, an electron discharge tubeamplifier having the input circuit thereof connected to .said antenna, arelay in the output circuit of said amplifier having a pair of normallyopen contacts and adapted to be energized when the antenna receives aradio wave of predetermined frequency, and a circuit including a sourceof potential and interconnecting the contacts of said relay and saidsolenoid for energizing the solenoid as the contacts are closed.

5. A rocket including a frame fixed relative thereto and having alongitudinal axis, means forming a combustion chamber, means forsupplying combustible material to said chamber for ignition therein toproduce expansive gases which impart directional inertia to the rocket,a nozzle secured to said chamber and forming an exhaust vent for saidgases to determine the direction of said directional inertia, resilientmeans pivotally mounting said chamber-forming'means and nozzle withinthe confines of said frame and normally maintaining said nozzle inalignment with said longitudinal axis, a plurality of electroresponsivedevices mounted at substantially equally spaced peripheral intervalsupon said frame and operable upon selective energization thereof tocorrelativelydeflect said chamber-forming means from said axis therebyto change the position of said nozzle with respect to said axisselectively in accordance with the energization of said devices, a radiowave sensitive antenna mounted upon said frame, a detector having theinput side thereof operatively connected to said antenna, an amplifyingmeans having the input side thereof connected to the output side of saiddetector, a plurality of relays connected in the output circuit of saidamplifying means whereby said relays are adapted to be selectivelyenergized when the antenna receives radio waves of predeterminedfrequencies, said relays being operatively connected to and controllingthe energization of said electroresponsive devices whereby the directionin which said nozzle points is controlled by the radio waves which havepredetermined frequencies and which reach the antenna.

6. A rocket including a frame fixed relative thereto and having alongitudinal axis, a jet propulsion motor, a nozzle fixed to said motorand forming an exhaust vent therefor, resilient means for mounting saidmotor Within the confines of said frame and normally maintaining saidnozzle in alignment with said longitudinal axis, magnetic means securedto said nozzle, a plurality of electromagnets mounted at equally spacedintervals around the periphery of said frame in close adjacency to saidmagnetic means and operable upon selective energization thereof to exertattractive forces on said magnetic means sufficient to defleet saidmotor and nozzle from said axis to predetermined angular settings withrespect to said axis, a radio wave receiving antenna mounted on saidframe, and circuit means interconnecting said antenna and saidelectromagnets, said circuit means including a source of electricalpower for energizing said electromagnets selectively in accordance withvariations in frequency of the radio waves reaching the antenna.

7. A rocket including a body with a fixed frame portion having alongitudinal axis, a jet propulsion motor, a nozzle fixed to said motorand forming an exhaust vent for said motor, resilient means mountingsaid motor within the confines of said frame portion and normallymaintaining said nozzle in alignment with said longitudinal axis,magnetic means secured to said nozzle, a plurality of electromagnetsmounted at equally spaced intervals around the periphery of said body inclose adjacency to said magnetic means and operable upon selectiveenergization thereof to exert attractive forces on said magnetic meanssufficient to deflect said motor and nozzle from said axis topredetermined angular settings with respect to said axis, a radio wavereceiving type antenna mounted on said body, radio wave detecting meansconnected to said antenna for detecting radio waves reaching saidantenna, first circuit means interconnecting said detecting means andsaid electromagnets, said circuit means including a source of electricalpower and a plurality of tuned relays for energizing said electromagnetsselectively in accordance with different selected frequencies of radiowaves which are detected by said detecting means, means forming achamber within said rocket body, an explosive charge disposed withinsaid chamber and adapted to be forcibly ejected therefrom, an initiallycompressed spring mounted in said chamber for ejecting said charge, alatch mechanism associated with said spring and adapted to normallymaintain said spring in compressed position and maintain said charge insaid chamber, a solenoid operatively associated with said latchmechanism and adapted when energized to operate said latch and therebyrelease said spring and charge, and second circuit means including asource of electrical power interconnecting said detecting means and saidsolenoid whereby the solenoid is energized and the charge is ejectedwhen the frequency of the radio waves reaching said antenna is of apredetermined value.

8. In apparatus of the character disclosed, in combination, a rocketbody with a fixed portion having a longitudinal axis, means forming acombustion chamber, a fuel tank mounted within said body, an exhaustvent at least a portion of which is composed of magnetic material andwhich is secured to said combustion chamber-forming means, resilientmeans pivotally mounting said combustion chamber and exhaust vent withinthe confines of said frame portion and normally maintaining said exhaustvent in alignment with said longitudinal axis fuel lines interconnectingsaid fuel tank with said combustion chamber, a plurality ofelectromagnets carried by said frame portion and arranged atsubstantially equally spaced intervals about said exhaust vent and inclose adjacency to the magnetic material portion thereof whereby each ofsaid electromagnets is operable upon energization thereof to exert anattractive force on said exhaust vent sufficient to deflect the exhaustvent to a different angular setting with respect to said axis, aplurality of tuned circuits each including a relay respectivelyconnected to said electromagnets for causing the actuation thereofselectively upon actuation of the associated relay, each of said tunedcircuits being tuned to a difierent predetermined response frequency ofradiant signal, signal receiving means carried by said body, meansinterconnecting said signal receiving means and said relays foroperating a selected one of said relays corresponding to a particularfrequency of signal when the signal comprises only one elementalfrequency thereby to effect one of a plurality of predetermined settingsof the exhaust vent corresponding thereto and for simultaneouslyoperating a plurality of relays corresponding to different predeterminedfrequencies of the signal simultaneously received by said signalreceiving means whereby additional settings of the exhaust ventintermediate said predetermined settings are effected.

References Cited in the file of this patent UNITED STATES PATENTS1,249,274 Chandler Dec. 4, 1917 1,319,068 Hammond Oct. 21, 19192,019,341 Dome Oct. 29, 1935 2,183,311 Goddard Dec. 12, 1939 2,257,277Righter Sept. 30, 1941 2,413,621 Hammond Dec. 31, 1946 2,414,898 RousJan. 28, 1947 2,462,069 Chatterjea et a1 Feb. 22, 1949 2,520,433Robinson Aug. 29, 1950 2,557,401 Agins June 19, 1951 FOREIGN PATENTS797,933 France Mar. 6, 1936 339,479 Italy Apr. 22, 1936

